Increasing the efficiency of turbine and compressor can be determined from the characteristics of fluid flow improvement especially in the body junction between the hub and the rotor-stator casing. One of the phenomena of fluid flow on the body junction is the presence of secondary flow caused by an imbalance between pressure and centrifugal force near the airfoil body. This secondary flow can lead the blockage effects and and destruction of energy flow. Some ways to delay flow separation among others using the turbulent generator turbulator. The existence of turbulator can increase the intensity of turbulence
so that the flow is more able to resist the adverse pressure gradient and friction effects. This research aims to study the characteristics of 3D flow separation across the body junction airfoil British 9C742.5C50 with and without the addition of Forward Facing Step Turbulator FFST. Airfoil geometry having a chord length 120 mm the distance to the airfoil FFST 23 C and step height h 4.8 mm. Analysis of shear stress line obtained from the Oil Flow Visualisation techniques OFV obtained experimentally using a wind tunnel with a Reynolds number 1.64x105. While the result was confirmed by analysis of the velocity
vector and pathline the distribution of pressure coefficient axial total pressure loss coefficient at the exit obtained numerically through software Fluent 6.3.26 with 3D models steady solver and k-e standard viscous model. To determine the diffectiveness of adding FFST studies varied with angle of attack 0 4 8 10 and 12. Addition FFST able to increase the intensity of turbulence so that the flow is more able to resist the adverse pressure gradient so can reduce losses caused by
secondary flow in the body junction of airfoil British 9C742.5C50. The
effectiveness of the addition of FFST occur at angle of attack 0 4 and 8. Highest reduction of axial total pressure loss at angle of attack 0 i.e 10.83. The results of this study can provide information about the flow phenomena in the field of body junction airfoil British 9C742.5C50 so it can be used as a consideration compressor inlet nozzle.

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